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Ultrahigh-precise guide star sensor attitude determination method

A sensor and guide technology, applied in astronomical navigation and other directions, can solve the problems of increasing computing time, inability to adapt, and difficulty in improving data update rate.

Active Publication Date: 2018-11-06
SHANGHAI ENG CENT FOR MICROSATELLITES
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Problems solved by technology

Since there are hundreds of millions of stars with a magnitude higher than 18 in the universe, sorting out the star catalog and cutting out the data will inevitably consume a lot of manpower and time; at the same time, the data volume of the star catalog often exceeds 40G; if it is stored in the guide star sensor in advance, To retrieve and match star positions in such a huge database, and then output ultra-high-precision attitude data, it is necessary to design a complex star map matching algorithm, and at the same time put forward extremely high processing power requirements for the processor, which not only increases the complexity of the algorithm, Increase the calculation time, and the data update rate is difficult to increase, which cannot meet the current requirements of satellite high-precision, high-stability and high-frequency attitude information output

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Embodiment Construction

[0012] The technical solutions of the present application will be clearly and completely described below in conjunction with the accompanying drawings and the embodiments of the present application.

[0013] Such as figure 1 As shown, the guide star sensor optical coupling device detector 1 (FGS CCD1) is designed on the upper and lower sides of the optical telescope (Visible Telescope, referred to as VT) optical coupling device (Charge-coupled Device, referred to as CCD) detector (VT CCD). And guide star sensor optical coupling device detector 2 (FGS CCD2).

[0014] VT coordinate system definition: take the center of the optical telescope optical coupling device detector (VT CCD) as the origin O, its row and column directions are the x and y axis directions respectively, and the z axis direction is determined by the right-hand rule.

[0015] The image point of a star Star on the FGS CCD1 through the optical lens is S 1 , B and C are image point S respectively 1 Mapping on t...

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Abstract

The invention relates to an ultrahigh-precise guide star sensor attitude determination method including the steps of: mapping the position of a mass center of an image point of a fixed star on FGSCCDonto a VT coordinate system; calculating attitude deviations in x-axis, y-axis and z-axis directions in the VT coordinate system; calculating relative attitude deviation quaternion; and calculating absolute attitude.

Description

technical field [0001] This application relates to an aerospace measurement and control method, in particular to a method for determining the attitude of an ultra-high-precision guide star sensor Background technique [0002] The star sensor (Fine Guidance Sensor) is a high-precision, high-reliability attitude measurement component widely used in aerospace vehicles today. The star sensor works in the real-time dynamic measurement mode, and its measurement accuracy is usually about 3 arc seconds. However, in order to achieve sub-arc-second attitude determination, that is, less than 1 arc second, the traditional star sensor can no longer meet its measurement accuracy requirements. [0003] In the existing technology, the Fine Guidance Sensor (FGS for short) that can achieve sub-arc second measurement accuracy needs to be completed by calling the huge star catalog database pre-stored in the guide sensor. Since there are hundreds of millions of stars with a magnitude higher th...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/02
CPCG01C21/02
Inventor 刘爽李东万松秦根健陈炳龙孙备李津淞方禹鑫
Owner SHANGHAI ENG CENT FOR MICROSATELLITES
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